Abstract: A brake for a bicycle includes a base, first and second arm assemblies. The first and second arm assemblies are pivoted to the base. The first arm assembly has a first end portion, for connection of a brake line a second end portion for frictionally contacting a brake side of a wheel rim. The second arm assembly is pivoted to the base and corresponds to the first arm assembly. The second aim assembly has a third end portion, a fourth end portion and a second abutting portion which is arranged on the third end portion. The second abutting portion is located correspondingly above the first abutting portion and interferable with the first abutting portion in a pivoting direction of the first abutting portion. The fourth end portion is swingable toward the brake side to clip the other brake side of the wheel rim.

Abstract: Provided herein is an electrically operated bicycle including a first frame, a second frame coupled to the first frame and including a seat, a first axle frame supporting a front axle connected to a front wheel and rotatably connected to one end of the first frame, a second axle frame supporting a rear axle connected to a rear wheel, a driving member configured to apply a driving force to at least one of the front wheel and the rear wheel, a battery pack electrically connected to the driving member, and an engagement member coupled to the battery pack and configured to fix the battery pack to at least one of the first frame and the second frame.

Abstract: The present invention relates to an electric bicycle frame and electric bicycle, the frame comprising a down tube with a housing defined therein into which an electric battery pack is inserted, the housing of the down tube having an insertion opening in its upper part for introducing the electric battery pack, such that the electric battery pack is concealed and protected inside the down tube of the frame with suitable accessibility for removal.

Abstract: A Motorcycle Engine Mount having Improved Stiffness. The device is a bolt-in replacement for the Original Equipment Manufacturer engine mounts for FXD_ series Harley Davidson motorcycles. The device has a single-piece, hardened steel outer frame, and a interstitial formed from urethane (rather than rubber) having a durometer reading of approximately 80. Unlike the device of the Parent Application, the urethane interstitial element is not bonded to the outer frame element so that the urethane interstitial element can be slid out of the outer frame and replaced, if desired. The interstitial element protrudes from the outer frame, and does not reach the full depth of the outer frame depth.

Abstract: An electronic shifting device and a bicycle using the same are provided. The electronic shifting device includes a primary controller, a first electronic derailleur unit, a second electronic derailleur unit, a cable, a main power supply and a first control unit. The first electronic derailleur unit is disposed adjacent to a first sprocket set, and the second electronic derailleur unit is disposed adjacent to a second sprocket set. The first electronic derailleur unit and the second electronic derailleur unit are configured to move a chain between a plurality of sprockets. The cable electrically connects the primary controller, the first electronic derailleur unit and the second electronic derailleur unit. The main power supply provides electrical power to the primary controller, the first electronic derailleur unit and the second electronic derailleur unit by the cable. The first control unit is configured for wirelessly transmitting a first control signal to the primary controller.

Abstract: There is provided a motorcycle. A crankshaft extends in a width direction of the motorcycle. A counter shaft is arranged in parallel with the crankshaft. A clutch mechanism is arranged at one end of the counter shaft and is configured to transmit and disconnect rotation of the crankshaft to and from the counter shaft. A clutch actuator is configured to perform a disconnection/connection operation of the clutch mechanism. A shift mechanism is arranged below the counter shaft and is configured to shift and transmit the rotation of the crankshaft to a driving wheel. A shift actuator is configured to perform a shift operation of the shift mechanism. The shift actuator is arranged opposite to the shift mechanism in a front and rear direction of the motorcycle with the clutch actuator being interposed therebetween.

Abstract: The present disclosure relates generally to knee braces for boats. The knee braces described herein are particularly suitable for use with lightweight, inflatable rafts and kayaks, for example packrafts used in backcountry boating. The knee braces include a fabric body and a plurality of adjustable straps configured to attach the fabric body to a side wall of the boat.

Abstract: A system is provided that includes a print head, a conveyance system, an encoding sensor, and at least one processor. The print head defines a print zone, and is configured to print on objects within the print zone. The conveyance system passes through the print zone, and is configured to translate a pallet through the print zone. The encoding sensor is disposed proximate to the conveyance system, and is configured to be oriented toward the pallet and to acquire positional information regarding the pallet. The at least one processor is operably coupled to the print head and the encoding sensor, and is configured to: receive the positional information from the encoding sensor; determine timing information corresponding to when a substrate disposed on the pallet will be in the print zone; and control the print head to print on the substrate when the substrate is in the print zone.

Abstract: The invention relates to a monohull drillship (1), comprising an elongated hull (2) extending in the length direction (3) of the drillship. Said hull (2) is provided with at least one open moon pool (4) arranged to be located at the waterline (5) during use of the drillship. The drillship (1) is arranged for multiple-activity operations, e.g. simultaneous drilling and casing handling, in such a manner that drilling equipment can be passed through said at least one moon pool (4) at at least two locations (7, 8), i.e. at at least two so-called well centres, which are spaced apart from each other in at least a direction (6) substantially transverse to the length direction (3) of the hull of the drillship.

Abstract: A wave-propelled or fluid-propelled vehicle, having a body extending from a nose portion to a tail portion and having a middle portion disposed between the nose portion and the tail portion; and at least one interior thrust cavity formed within at least a portion of the body, wherein each interior thrust cavity extends from a cavity inlet aperture formed proximate the tail portion to a back wall. A cavity outlet aperture may optionally be associated with each thrust cavity, such that each cavity outlet aperture is formed proximate the back wall and is in fluid communication with the cavity outlet aperture, via the interior thrust cavity.

Abstract: The present application is directed to a selectively deployable fin system which includes at least one housing positioned within a body of a standup paddleboard, the housing defining at least one housing passage therein, at least one actuator is positioned within the housing. The actuator is con figured to be operable by a user positioned on the standup paddleboard or similar watercraft during use. At least one linkage system, in communication with the actuator, is positioned within the housing. In addition, at least one fin is in communication with the actuator via the linkage device. The fin is configured to be selectively positioned within the housing in a retracted configuration and selectively extending from the housing in a deployed configuration.

Abstract: The invention is a vehicle control system which is envisaged to be used in high speed planing watercraft which has a means of control about three axes where the invention controls the said watercraft about at least two axes by actuating control surfaces. The invention uses a microchip based processor (1) to actuate control surfaces based on input from various sensors (3). The invention also uses a three dimension time of flight imaging subsystem (8) to read information of the oceanic wave conditions.

Abstract: The present invention contributes to vessel navigation safety, by applying conventional navigation technology and using smartphones or other wireless communication terminals to provide a chart according to vessel type. Provided is a server system 3, which: receives, from wireless communication terminals 2 which are carried by users aboard vessels 4, position information of the wireless communication terminals 2 and information of the sizes of the vessels 4; creates, in response to the sizes of the vessels 4, navigation trajectory information formed from time series position information of the vessels 4; and, with the navigation trajectory information as an input, updates navigable course information for each size of the vessels 4.

Abstract: The present invention surveils a ship and automatically detects movement around a ship such as, for example, a man overboard condition. Detection is achieved using a continually scanning set of lasers that cooperate with long-wave infrared thermal imaging cameras that are used to classify the movement. If a MOB event is determined, an alarm is then initiated on the bridge of the ship.

Abstract: A flying underwater imager device operates in two modes, a tow mode and a free fly mode. In the tow mode for locating underwater objects, the imager device opens foldable wings for remaining depressed below the surface when the wings generate a negative buoyancy. Otherwise, neutral buoyancy characteristics bring the imager device back to surface. In the free fly mode for approaching and imaging underwater objects, the imager device closes the foldable wings and uses thrusters for moving into position to image the underwater objects.

Abstract: A ship is configured to obtain propelling force by driving a designed propeller with a main engine. A vertical tunnel is formed at a bow portion to pass through a ship bottom. A lateral tunnel is formed in communication with the vertical tunnel. An additional propeller device has an additional propeller and a driving unit for the propeller. The additional propeller device is configured such that the additional propeller can turn around a vertical center line of the vertical tunnel. The additional propeller is configured to be capable of vertically movable from below the ship bottom to a height position of the lateral tunnel. When the additional propeller is at the height position of the lateral tunnel, the additional propeller is configured to follow the lateral tunnel.

Abstract: A method of controlling engine RPM in a marine propulsion device having an engine that effectuates rotation of a propulsor through a gear system that shifts amongst a forward gear position, a reverse gear position, and a neutral position, includes determining that a coolant temperature is below a temperature threshold or that a battery voltage is below a voltage threshold, and then increasing an engine RPM setpoint by a compensation RPM amount while the engines remains in an idle state in order to increase the coolant temperature or the battery voltage. When a shift instruction is detected to transition the gear system from the reverse gear position to the neutral position or from the forward gear position to the neutral position, the engine RPM setpoint is reduced by a shift RPM reduction amount during transition of the gear system, and the engine is controlled according to the engine RPM setpoint.

Abstract: A solar-powered airship with a hull configured to contain a gas and at least one propulsion assembly with a propulsion device and electric motors configured to drive the propulsion device. The airship may also include a power supply system including solar panels operatively coupled to the electric motors and configured to supply power to the electric motors. The power supply system may also include batteries operatively coupled to the solar panels and configured to receive and store electrical energy supplied by the solar panels, the batteries being further operatively coupled to the electric motors and configured to supply power to the electric motors. The batteries may each be located within an outer envelope of the airship defined by the hull of the airship in a position selected to provide ballast. The solar-powered airship may also include a cargo system configured to contain passengers or freight.

Abstract: A rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel, the structural stiffened panel comprising a stressed skin and a stiffening framework that is rigidly attached to the stressed skin, wherein the stressed skin comprises an inner skin, an outer skin and a core element assembly that is arranged between the inner skin and the outer skin, the core element assembly comprising at least one viscoelastic core element and at least one intermediate core element that are tessellated, wherein the at least one viscoelastic core element is provided for noise and vibration damping.

Abstract: A device for fireproofing a section of a structural part made of composite material. The device includes a skin having an outer surface configured to face the flame and an inner surface. The skin is made of composite material that includes fibrous reinforcement in a polymer matrix. The skin includes a fastener to fasten the part to the structure. The device includes a layer of needled mineral felt placed between the inner surface of the skin and a surface of the structural part.

Abstract: An inflight connection system for aircraft having at least one wing with a wingtip includes, for each aircraft, a primary connector selectively extendable from the wingtip, an alignment connector selectively extendable from the wingtip and a male and female connector assembly disposed proximate the wingtip. The primary connectors extend a greater distance from the wingtips than the alignment connectors such that the primary connectors form a first connection between the aircraft when the aircraft are flying in a connection pattern. Thereafter, retraction of the primary connectors reduces wingtip separation of the aircraft such that the alignment connectors form a second connection between the aircraft establishing coarse alignment therebetween. Thereafter, retraction of the primary and alignment connectors further reduces wingtip separation of the aircraft such that the male and female connector assemblies form a third connection between the aircraft establishing fine alignment therebetween.

Abstract: An apparatus and method are provided for a shape adaptive airfoil configured to be coupled with a tip of an airplane wing. In one embodiment, the shape adaptive airfoil is a blended winglet comprised of a base section coupled with the airplane wing, a blade section projecting in a vertical direction above the base section, and a radius section interconnecting the base and blade sections. Adaptive control structures may be incorporated into leading and trailing edges of the base section and the blade section. The adaptive control structures of the base section may facilitate changing a camber profile of the shape adaptive airfoil. The adaptive control structures of the blade section may enable changes to a toe angle of the blade section.

Abstract: The present invention includes an air flow bypass for a tiltrotor engine comprising: a ram air inlet comprising bypass door(s) capable of at least partially or fully blocking a ram air flow through the ram air inlet; a barrier filter inlet positioned in a side, a bottom, and/or a top of a tiltrotor engine nacelle; a filter plenum; a selector duct comprising one or more openings; and one or more selector duct doors or covers over the one or more openings; wherein the barrier filter inlet, the filter plenum, the one or more openings in the selector duct, the selector duct, and an engine are in fluid communication and the bypass door(s) in the ram inlet are closed and the barrier filter inlet provides filtered air flow to the engine when the aircraft is in hover operations.

Abstract: A motor assembly that includes a motor having a motor casing, a rotatable shaft extending from said motor casing to a shaft length and a hub coupled to said rotatable shaft, the hub having a circumferential skid surface disposed immediately proximal to the motor casing and having a channel configured to seat a propeller, when a propeller is present, wherein a bending moment applied to the shaft through the hub results in the circumferential skid surface contacting said motor casing.

Abstract: A variable pitch propeller is designed to adjust the pitch of the propeller blade during flight to maximize the propeller efficiency. The propeller blade may comprise airfoil cross-sections. Each cross-section may be composed of different materials at the leading edge and trailing edge. In various embodiments, these materials are selected and oriented to achieve the necessary elastic moduli of the leading and trailing edge for the airfoil cross-section. During liftoff, the airfoil at the blade tip possesses a high blade pitch (e.g. 20 degrees), thereby increasing the generated lift on the propeller blades. During flight or hover conditions when maximal lift is no longer required, the trailing edge of the airfoil displaces upward and reduces the blade pitch to minimize the drag forces on the blade tip.

Abstract: A system changes the pitch of blades of at least one turbine engine propeller provided with a plurality of blades. The system includes a link mechanism connected to the propeller blades at a first interface, and a control means acting on the link mechanism and having a body movable in translation along a longitudinal axis. A load transfer module is arranged between the link mechanism and the control means. The load transfer module is connected to the link mechanism at a second interface. The system further includes means for adjusting the setting of the blades, the adjustment means having first adjustment elements configured to adjust an axial position of the second interface along the axis. The adjustment means also includes second adjustment elements configured so as to adjust an axial distance along the axis between the first interface and the second interface.

Abstract: The invention relates to turbine engine module (1) including a case (9) rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case (15) comprising a cylindrical wall (16) extending between an inner wall (17) and an outer wall (18) of the rotating case (9), and a system (26) for changing the pitch of the blades (14) of the propeller. The wall (16) is connected downstream to a first substantially frustoconical wall (42) and upstream to a second substantially frustoconical wall (41), a first rolling bearing (19) being inserted respectively downstream directly between a radially outer face (21) of the inner wall (17) and a radially inner face (23) of the first frustoconical wall, and a second rolling bearing (19?) inserted downstream directly between the radially outer face (21) of the inner wall (17) and an inner face (43) of the second frustoconical wall (41).

Abstract: A system is configured to change the pitch of blades of at least one turbine engine propeller provided with multiple blades. The system includes a control means acting on a connecting mechanism connected to the blades of the propeller. The control means includes a stationary body and a movable body translatable along a longitudinal axis (X) relative to the stationary body and defining two chambers. A fluid supply means is configured to be connected to a fluid supply source and to supply the chambers. The fluid supply means includes at least one channel. The channel is arranged and extends along an axis (Q) parallel to the longitudinal axis in an overthickness of a wall of the stationary body, the overthickness extending radially inside relative to the longitudinal axis.

Abstract: A method of controlling an elevator of an aircraft includes selecting a factor for increasing or decreasing a predetermined horizontal tail load alleviation (HTLA) authority limit for an elevator based on at least one aircraft parameter. The HTLA authority limit decreases with an increase in Mach number and/or airspeed. The method also includes computing an elevator position limit as a product of the HTLA authority limit and the factor, and moving the elevator to a commanded elevator position that is no greater than the elevator position limit.

Abstract: The invention relates to a flight control device for an aircraft, including a connection lever, mechanical means for limiting an angular stroke of the connection lever, first means for generating force feedback on the connection lever about said pivot axis, second means for generating force feedback on the connection lever, which means are arranged in parallel with the first means, at least one element selected from the second means and the connection lever comprising mechanical means for connecting them together temporarily, which means are arranged to be active when the connection lever is moved beyond a predetermined angular position in the angular range so that the second means are connected to the connection lever.

Abstract: A device and method for flying an aircraft is disclosed. A housing that is removably installable in a cockpit of the aircraft is installed in the cockpit. The housing includes a processor. The processor receives a flight measurement from the aircraft, determines a flight control parameter for flying the aircraft from the flight measurement, and operates a flight control device of the aircraft to implement the flight control parameter to fly the aircraft.

Abstract: Example active flow control systems and methods for aircraft are described herein. An example method includes supplying pressurized air to a plurality of nozzles. The nozzles arranged in an array across a control surface of an aircraft, and the nozzles are oriented to eject the pressurized air in a substantially streamwise direction. The method further includes activating the nozzles to eject the pressurized air in sequence to create a wave of air moving in a spanwise direction across the control surface.

Abstract: The present disclosure is directed to a low-distortion inlet assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet assembly includes a plurality of structural members, such as struts or strakes, mounted at predetermined locations around a circumference of the fan shaft of the fan at the inlet. The predetermined location(s) may be determined as a function of swirl distortion entering the inlet. As such, the structural member(s) are configured to reduce swirl distortion of the airflow entering the fan. In some embodiments, the inlet assembly may also include inlet guide vanes. In alternative embodiments, the inlet assembly may be absent of inlet guide vanes.

Abstract: The present disclosure is directed to a low-distortion inlet assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet assembly includes a plurality of structural members mounted at one or more predetermined locations around a circumference of the fan shaft of the fan. More specifically, the predetermined location(s) has a swirl distortion exceeding a predetermined threshold. Further, the inlet assembly includes at least one airflow modifying element configured within the inlet so as to reduce swirl distortion entering the fan.

Abstract: A remote hydraulic system for an aircraft may provide hydraulic fluid to nose landing gear while being isolated from the main landing gear and other main hydraulic systems of the aircraft. A supply pressure accumulator may be configured to supply hydraulic fluid to a hydraulic load of the nose gear. A pressure sensor may be configured to detect a hydraulic pressure in the supply pressure accumulator. A pump may be in fluid communication with the supply pressure accumulator and configured to switch on in response to the hydraulic pressure below a threshold value. A return pressure accumulator may be configured to store the hydraulic fluid returning from the hydraulic load. The pump may drive fluid from the return pressure accumulator to the supply pressure accumulator.

Abstract: An aircraft tire includes a tire body forming an outer peripheral part of an aircraft wheel; and a protrusion with a pressure receiving surface configured to receive flight wind pressure toward one end and a streamline shape tapering toward another end. The protrusion rotates the aircraft wheel before touchdown through flight wind pressure received by the pressure receiving surface. The protrusion includes a pair of legs; a weight portion with a center of gravity positioned outwardly of respective horizontal positions of the pair of legs with respect to a center line widthwise of the tire body; and a hollow part extending between the ends of the protrusion. Centrifugal force that acts on the weight portion causes the pair of legs to fall over in a direction toward an outer periphery of the tire body to narrow the hollow part for reduction of an area of the pressure receiving surface.

Abstract: A ground movement plug-in (GMP) apparatus for providing ground propulsion to an unmanned aircraft vehicle (UAV). In an embodiment, the GMP apparatus includes a frame configured to mechanically couple with the UAV, a plurality of wheels, at least one of which is actuatable by a motor, and a controller operably coupled to the motor to control propulsion of the GMP apparatus.

Abstract: Aircraft landing gear (1) comprising: an axle shaft (2); a strut (3) extending along a main strut axis (Z) and having a first part (3a) carrying the said axle shaft (2) and a second part (3b); a main damper (5) designed to damp axial movements of the first strut part (3a) with respect to the second strut part (3b); a first secondary damper (6a) distinct from the said main damper and designed to damp a movement of angular oscillation, about the axis (Z). The first secondary damper (6a) is carried by the first strut part (3a) and comprises: an inertial mass (M); and means (7a) of connecting the inertial mass (M) to the first strut part (3a) which means are designed to damp rotational movements of this inertial mass (M) about the axis (Z).

Abstract: A method of forming a balanced rotor blade assembly includes measuring a weight of a plurality of sub-components of the rotor blade assembly excluding a core. A configuration of a core of the rotor blade assembly is determined. In combination, the core and the plurality of sub-components achieve a target weight distribution and moment. The core is then fabricated and assembled with the plurality of sub-components to form a rotor blade sub-assembly.

Abstract: A flight device includes a device body with a surface, a plurality of arm structures disposed in the device body and a plurality of rotor modules disposed to the arm structures respectively. Each arm structure includes a fixing base, a second screw element, a connecting unit, a rod body and a position-limiting element. The fixing base is disposed in the device body and includes a first screw element having a first screw part. The second screw element has a second screw part matched with the first screw part. The connecting unit drills through the second screw element. The connecting unit is locked to the fixing base by screwing the first and second screw parts with each other. The rod body drills through the connecting unit. The position-limiting element is disposed between the second screw element and the connecting unit. The position-limiting element abuts against the second screw element.

Abstract: Aerial vehicles may include propulsion units having motors with drive shafts that may be aligned at a variety of orientations, propellers with variable pitch blades, and common operators for aligning the drive shafts at one or more orientations and for varying the pitch angles of the blades. The common operators may include plate elements to which a propeller hub is rotatably joined, and which may be supported by one or more linear actuators that may extend or retract to vary both the orientations of the drive shafts and the pitch angles of the blades. Operating the motors and propellers at varying speeds, gimbal angles or pitch angles enables the motors to generate forces in any number of directions and at any magnitudes. Attributes of the propulsion units may be selected in order to shape or control the noise generated thereby.

Abstract: Apparatus for vertical or short takeoff and landing, and operational control during flight. In one embodiment, the apparatus includes a main body assembly, the main body assembly including: a fuselage, the fuselage includes one or more power motor assemblies and one or more actuator motor assemblies; a plurality of power mounting bodies and a plurality of power/articulation mounting bodies; a static rail that is operatively coupled with the plurality of power mounting bodies; a transient rail that is operatively coupled with the plurality of power/articulation bodies; and a plurality of airfoils, each of the plurality of airfoils being coupled to a respective power/articulation mounting body. Various sub-systems of the apparatus and methods of manufacture and use are also disclosed.

Abstract: A caul assembly includes a semi-rigid caul plate formed in a shape complementary to a portion of a component receivable therein and a heater located at an exterior surface of the semi-rigid caul plate. The heater is adapted to apply heat to a localized portion of the component.

Abstract: A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force.

Abstract: A control system for controlling at least collective pitch of rotor blades, of a multi-blade rotor with a rotor shaft in a rotary-wing aircraft, the control system comprising a non-rotating sliding sleeve that is mountable to the rotor shaft such that the non-rotating sliding sleeve is axially displaceable coaxially to an associated rotor axis on the rotor shaft, at least one actuator arm that is pivotally mounted to the non-rotating sliding sleeve and adapted for axially displacing the non-rotating sliding sleeve that is mounted to the rotor shaft upon activation, and at least one hinge support that is adapted for a hinged support of the at least one actuator arm.

Abstract: In some embodiments, a rotorcraft includes a fuselage, a tailboom, a drive system and a variable thrust cross-flow fan system. The cross-flow fan system includes a cross-flow fan assembly that is mechanically coupled to a drive shaft and operable to rotate with the drive shaft about a longitudinal axis. The cross-flow fan assembly includes first and second driver plates having a plurality of blades rotatably mounted therebetween. The blades are disposed radially outwardly from the longitudinal axis and have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis. The blades are moveable between a plurality of pitch angle configurations. A control assembly is coupled to the blades. The control assembly is operable to change the pitch angle configuration of the blades to generate variable thrust at a substantially constant rotational speed of the cross-flow fan assembly.

Abstract: In one aspect, there is provided an aircraft, including a fuselage having a longitudinal axis extending from a front portion through an aft portion; first and second tail members extending from the aft portion; a first cross-flow fan system rotatably mounted to the first tail member; and a second cross-flow fan system rotatably mounted to the second tail member. The first and second cross-flow fan systems are configured to provide a forward thrust vector and an anti-torque vector on the aircraft. The first and second cross-flow fan systems can have a rotational axis oriented generally vertically. In another aspect, there is an aircraft including a fuselage having a front portion and a tail portion; and a cross-flow fan system supported by the tail portion. Embodiments include a cross-flow fan system retrofittable onto an aircraft and methods for retrofitting an aircraft with a cross-flow fan system.

Abstract: An aircraft includes a wing where a first rotor and a second rotor are coupled to the wing at a fixed position relative to the wing. The aircraft also includes a fuselage and a bearing. The bearing mechanically couples the wing and the fuselage and permits the wing and the fuselage to rotate with respect to each other about an axis of rotation. The bearing permits the fuselage to rotate under the influence of gravity to be in a same orientation relative to ground when the wing is in a first orientation relative to the ground as well as a second orientation relative to the ground.

Abstract: An aspect provides an aircraft including a fuselage and a cross-flow fan system attached to the fuselage. The cross-flow fan system including a cross-flow fan assembly associated with a rotatable wing member having an exterior aerodynamic surface. In one aspect, there is provided an aircraft with a fuselage having a forward portion and an aft portion; a first cross-flow fan system rotatably attached to the left side of the forward portion of the fuselage; a second cross-flow fan system rotatably attached to the right side of the forward portion of the fuselage; a third cross-flow fan system rotatably attached to the left side of the aft portion of the fuselage; and a fourth cross-flow fan system rotatably attached to the right side of the aft portion of the fuselage.

Abstract: A variable thrust cross-flow fan system for an aircraft including a rotatable wing member having a first housing member; an actuator assembly operably coupled to the first housing member; and a variable thrust cross-flow fan assembly including a first and second driver plates having a plurality of blades rotatably mounted therebetween. The plurality of blades has a circular path of travel when rotating and includes a control assembly coupled to the plurality of blades to generate a variable thrust force. The control assembly includes a control cam that is substantially non-rotatable relative to the first and second driver plates and a hinge member that is fixedly connected to the control cam and to the first housing member at a hinge axis. Rotation of the first housing member by the actuator assembly imparts rotation of the control cam about the hinge axis, thereby changing the direction of the variable thrust force.